Aeroplane



March 3, 1931. v wATTER 1,794,814

AEROPLANE Filed March 20, 1928 3 Sheets-Sheet 1 INVENTOR Mwlzael Wattw;

BY MmQL ATTORNEYS March 3, 1931. M. WATTER 1,794,814

AEROPLANE Filed March 20, 1928 s Sheets-Shet 2 25 2410 55 52 l W A A W ,V

v INVENTORVV6 Mid/Mel Wattez;

BY Z 51mm .-ATTORNIE M. WATTER March '3, 1931.

AEROPLANE 5 Sheets-Sheet 3 Filed March 20, 1928 INVENTOR ATTORN EYS Patented Mar. 3, 1931 UNITED STATES PATENT OFFICE- MICHAEL WATTER, OF NEW YORK, N. Y., ASSIGNOR TO CHANGE M. ITOUGHT, OF GREN- WOLDE, GREAT NECK, NEW YORK AEROPLANE Application filed March 20, 1928. Serial No. 268,069.

This invention relates to aircraft and particularly to aeroplanes of the amphibian type. The object of the invention is a retractable landing gear which is so constructed and as- Q sociated with the floating structure of a hydroaeroplane or flying boat that it may be retracted or lowered with marked facility while in flight. A further object of the invention is a landing gear of this general character including amounting and operating mechanism which is characterized by its simplicity in construction and operation, and which may be mounted upon the floating structure with a minimum of modification of the standard float or boat, such for example as a float or boat of the V bottom type. More particularly I have devised a retractable landing gear which is attached directly to the keel structure of the boat, and preferably to the side at a point or points above the chine, in such manner that the gear may be lifted and lowered by moving the connection with the keel structure laterally thereof between the keel and the chine.

For a better understanding of the invention, reference may be had to the accompanying drawings forming a part of this application wherein- Fig. 1 illustrates an aeroplane embodying my invention,

Fig. 2 is a rear view of the floating structure and associated landing gear with parts of the craft removed-for convenience in illustration,

Fi 2a is a detail of the strut connections, showing the shock absorber,

Fig. 3 is a detailed view,

Fig. 4 is a sectional view along the line 4-4 of Fig. 3,

Fig. 5 is a view corresponding to Fig. 3 showing the arts in a different position,

Fig. 6 is a view along the line 6-6 of Fig. 5,

Fig.- 7 .is a view corresponding to Figs. 3 and 5 in still another position of the mechanism, and

Fig. 8 is a side view of the float and landing gear.

Referring to the. drawings, I have indicated my invention as embodied in a hydroaeroplane having a central floating structure 1 and having wingtip balancing floats 2, the floating structure 1 being disposed beneath the fuselage or main body 3 of the craft. The float structure 1 is indicated as having a standard step 4 in the bottom thereof. The landing gear includes a wheeled axle 5 on each side of the central floating structure 1 and each axle is connected to the float by means of a pair of struts 6 and 7 arranged in the form of a V and pivotally connected to the axle 5 near its outer end at the point 8. These struts 6 and 7 diverge upwardly from the lowered position of the landing gear and are pivotally connected at the fore and aft alined points 6' and 7 to the side of the floating structure, preferabl above the chine 9, one of these struts, as or example the forward strut 6, being of the shock absorber type or containing a yielding spring mechanism.

In the lowered position of the landing gear the inner ends 5 of the axles are rigidly connected to the bottom of the float at a point or structure, by means of'the intermediate slide blocks 10. These slide blocks 10 are adapted to travel in runways 11 secured to the V float bottom and are lockable in their limiting positions as for example to the keel structure and to the sides or chine structures in any suitable manner. I have indicated diagrammatically in 2 a means 12 for looking the slide blocks 10 to the keel structure and means 13 for locking them to the chine structures of the V bottom. Each wheeled axle 5 is pivoted to the slide block 10 as indicated for vertical pivotal movements and up on the outward movement of the slide block along its runway 11 the wheel and its axle is lifted to the elevated position as indicated in Fig. 2 by the strut 6 and 7 pivoting about the longitudinal axis 6, 7 I have indicated the blocks as movable by means of a system of cables, each block having two cables attached thereto or having the ends of a single cable attached thereto, which cable passes over the pulleys 15, 16, 17, 18 and 19 and these cables are operable by a Windlass 20 or any other suitable means whereby the operator or pilot may simultaneously actuate the slide blocks 10 to move them outwardly along the runways or inwardly to lock them rigidly to the central bottom structure or keel structure. In Fig. 2 the cable having its ends attached to the right hand slide block is indicated at 21, while the cable attached to the left hand slide block 10 is indicated at 22.

I have indicated diagrammatically in Fig. 2 the structure and control arrangement of the amphibian and in Figs. 3-7 I have indicated in more or less detail one embodiment of the slide block 10, the runway 11 and the means for locking the slide block at the ends of its travel, but it is understood that these parts may assume other forms than those particular ones illustrated. Referring to these drawings, the carriage or slide block 10 is provided with the beveled feet or base 24 which slide in correspondingly shaped transverse grooves or guide ways formed in the bottom of the floating structure or in the runway 11 secured to the bottom of the floating structure, This runway 11 may be conveniently formed by means of a bottom plate 23 and side rails 23' secured thereto, the plate 23 having grooves formed therein and the rails being beveled oif to accommodate the beveled of! feet 24 of the slide block connection or carriage. The slide block 10 is provided with a transverse slot or guide 26, this slot being slightly inclined to the vertical or at right angles to the bottom. This slot serves as a runway or guide for a locking pin or bolt 27. The locking bolt 27 is movable up and down in the guide way 26 and is actuated by a bell crank lever 28, this lever having a fork 29 straddling the intermediate portion of the locking pin 27 and being pivoted at 30 to the slide block on the pivotal axis of the axle 5. The lever 28 has an arm 31 projecting from the fork 29 and this arm carries a roller 32 which, in any other position but the operative lowered position of the axle 5, engages the bottom of the boat structure or rather the plate 23 and tilts the fork 29 into a position to hold the locking pin 27 in the upper part of the guide 26 (Fig. 5). In the locked lowered position, however, this roller 32 enters a recess 33 formed in the bottom of the boat or plate 23 and this permits the locking bolt 27 to drop or be carried to the bottom of its guide. Rigldly fixed to the central bottom or keel structure of the boat is a double bracket 35, indicated as integral with rails 23 and depending down therefrom, this bracket having formed on its inner sides grooves 35 registering with the guide Ways 26 for the accommodation of the heads of the locking bolt 27 and also on either side there is a keeper 36 with a beveled ofit' front edge 37, permitting the locking bolt heads to pass over into the grooves 35' for engagement with the keepers. The keepers '36 firmly and rigidly hold the slide block 10 in the innermost position. The free ends of the cable 21 are attached to the end of the arm carrying the roller 32. as for example to the axle of the roller 32, and by pulling upon the cable 21 to the right,

as indicated by the arrow in Fig. 3, the first movement results in the tilting of the bell crank lever 31 to ,lift the locking bolt 27 from engagement with the keepers 36 and above the lever thereof, whereupon the carriage or slide block 10 is then free to be moved outwardly to elevate the landing gear, Fig. 5 indicating an intermediate position. This movement is continued until the locking mechanism 13 near the float chine is reached, whereupon the slide block is automatically locked in this position. This locking mechanism includes a double bracket 40 fastened to the float bottom at the chine, straddling the slide block 10'and containing transverse recesses 41 in their inner ends parallel to the guide way 26 in the slide block 10 which rectangular recesses 41 are adapted to receive the squared ends of the locking bolt 27 In advance of the recesses 41 the bracket mem ber 40 is provided with the cam surfaces 42, which cam surfaces engage the squared ends of the locking bolt 27 as the slide block moves up and cause the bell crank lever 28 to turn about the axis 30 against the pull of the cable 21, the roller 32 being elevated above the level of the runway plate 22 and the latter being cut away at 43 to permit the turning of the lever when the bolt 27 rides upthe cams 42. When the locking bolt 27, therefore, reaches the recesses 41, it is automatically forced thereinto by the pull of the cable 21 which turns the bell crank lever about the axis 30 and lifts the bolt to the top of the guide slide 26 and into the recesses 41. The landing gear is automatically disengaged from the locking bracket 40 when the pilot or operator pulls oppositely by means of the left hand cable 21 to turn the bell crank lever 28' about its pivotal axis 30 in the opposite direction (counterclockwise, Fig. 7) to carry the locking bolt 27 toward the bottom of its guide slot and out of recesses 41 of the locking bracket. The slide block then is free to move in the opposite direction along its raceway to lower the landing gear, the weight of the landing gears facilitating this movement which is effected by the pull on the cable 21 in the proper direction. When the slide block gets to the inner locking position at the keel the roller 32, upon passing into the recess 33, permits the bell crank lever to be pulled over by the cable 21 to cause the locking pin 27 to engage the lock or keepers 36. The bracket 40 extends around the chine of the floating structure and embraces the side thereof, carrying the pulley 17. The landing gear is identical for both sides, and a descrip- The operation of the landing gear is clear from the above description. By merely pulling on the cables 2122 simultaneousl in opposite directions from the center, 0th landin gear axles 5 are lifted and by lpulling towar the center or keel structure t ey are lowered, and the gears are automaticall locked in both the lowered and lifted positions. In the particular embodiment shown the struts 6 and 7 are rigidly fastened together at their outer ends so as to form a rigid unit, with the shock absorbin mechanism 60 contained in the strut 6 (see ig. 2a) and accordingly, each gear moves in a plane at right angles to the axis 6"7'.

It is understood that the invention is alpplicable to h droaeroplanes of either t e single or dou le float t pe or to planes of either the pontoon or the flying boat type, and many of the features of the invention disclosed are applicable to retractablelanding gears generally, whether on water craft or land machines. In the particular embodiment shown, the floating structure is indicated of the V-bottom type, but floating bodies of differently shaped bottoms may be employed. It is obvious also that instead of wheels, skid structures may be employed of the retractable type.

I claim: I

1. In an amphibian aeroplane, a floating and hydroplaning body and a retractable landing gear on one side of said floating body and normall connected with the keel structure thereof at readily disconnectabletherefrom and attachable thereto.

2. In an am hibian aeroplane a floatin and hydroplaning body, a retractable lam ing gear on one side of said floatin body and normally connected with the kee structure thereof, and a readily detachable connection therefor which is movable away from the keel structure and movable to another part of the hull structure.

3. In an amphibian of the character setv forth in claim 2 wherein the detachable connection is attachable to the hull chine in the retracted position of the gear.

4. In an amphibian of the character set forth in claim 2 wherein the detachable connection is inthe form of a sliding member and the hull bottom is provided with a run- -keel structure of the body way for said connection together with means for automatically lockin and unlocking the landing gear to and wit the keel structure by the act of moving the detachable connection to and from the keel structure.

5. In an amphibian of the character set forth in claim 2 wherein the detachable con nection is in the form of a sliding member and the hull bottom is Y-shaped and provided with a runway for said connection from the keel structure to the chine together with means for moving the detachable connection to and from the keel structure and automatic means responsive to said moving means for locking and unlocking the detachable connection when the movlng means is actuated.

6. In an amphibian aeroplane, a floating and hydroplaning body, a retractable landin'g gear on one side of said floating body includin a wheeled axle having a readily detachalfie and movable connection with the at its inner end and being pivotedto the slde of the body for up and down adjustments by means of a strut pnlroted nearer the outer end of the wheeled ax e.

7. An aero lane of the character set forth in claim 6 w erein the wheeled axle is pivoted to the side of the floating body up above the chine thereof at points spaced in a fore and aft direction.

8. 'In an aeroplane of the character set forth in claim 6 wherein the detachable and movable connection with the underbody structure is in the form of a slide member which is movable and attachable to another part of the body for adjusting the landing gear.

9. In an aeroplane of the character set forth in claim 6 wherein the detachable and movable connection with the keel structure is in the form of a slide member and the floating body bottom is provided with a transverse runway from the keel structure to the chine along which the sliding connection is movable.

10. In an aeroplane of the character set forth in claim 6 wherein the floating body has a V-shaped bottom, the detachable and movable connection is in the form of a sliding member, the V bottom is provided with a transverse runway extending to the chine along which said sliding member is movable, and means for holding the slide member at the chine. V

11. In an aeroplane of the character set forth in claim 6 wherein the floating body has a V-shaped bottom, the detachable and movable connection is in the form of a sliding member, the V bottom is provided with a transverse runway extending to the chine along which said sliding member is movable, and automatic locking means for automatically locking the sliding member to the underbody at one end and automatically locking the same to-the chine structure at the other end of the runway.

12. In an aeroplane of the character set forth in claim 6 wherein the floating body has a V-shaped bottom, the'detachable and movable connection is in the form of a sliding member, the V bottom is provided with a transverse runway extending to the chine along which said sliding member is movable, and automatic locking means for automaticall locking the sliding member to the un-.

der ody structure at one end and automatically locking the same to the chine structure at the other end of the runway, including cables attached to the op osite sides of the sliding members operable by the pilot.

13. In an aeroplane of the character set connection to the normal connection point,

means for moving thedetachable connection and means responsive to the moving means for operating the locking bolt and keeper.

15. In an aeroplane of the character set forth in claim 14: wherein the locking bolt and keeper mechanism includes a keeper at the normal connection point and another keeper at a remote point.

16. In an aeroplane of the character set forth in claim 14 wherein a cam is provided adjacent the keeper at the remote point which engages the bolt and actuates it against the force of the moving means to cause the automatic engagement of the bolt with the keeper by the act of moving the detachable connection in that direction.

17. In an aeroplane of the character set forth in claim 14 wherein the means for locking the bolt and keeper mechanism includes a pivoted lever which at the normal point of connection occupies a position to cause the bolt and keeper to be operatively engaged but when thevmovingmeans is actuated is caused to actuate the bolt and keeper mechanism to disen age the same and permit the movement of. t e detachable connection.

18. In an aeroplane of the character set forth in claim 14 wherein the means for locking the bolt and keeper mechanism includes a pivoted lever which at the normal point of connection occupies a position to cause the bolt and keeper to be operatively ated is caused to actuate the bolt and keeper mechanism to disen age the same and permit the movement 0 the detachable connection, said lever carrying a roller which occu- Y engaged, but when the moving means is actu- 

